Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

摘要: Abstract Supersonic flutter control of a three-layered sandwich curved panel rectangular plan form with an adaptive electro-rheological fluid (ERF) core layer is investigated. The excited by arbitrary transient transverse load along airflow yaw angle. problem formulation based on Kirchhoff–Love thin shell theory, the first order Kelvin–Voigt viscoelastic material model, and linear quasi-steady Krumhaar's modified supersonic piston theory that accounts for both curvature flow classical Hamilton's principle Galerkin method are used to set up equations motion which then put in state-space form. effects applied electric field, aspect ratio, shallowness angle, direction critical free stream static pressure studied. Also, aeroelastic response cylindrical impulsive central point calculated using Runge–Kutta time integration scheme. Subsequently, Sliding Mode Control (SMC) methodology implemented actively attenuate structural regime. Numerical simulations establish effectiveness configuration successful suppression oscillations. validity results demonstrated rigorous comparisons existing data.